Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated mehtods

ABSTRACT

Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.

TECHNICAL FIELD

The present invention is directed generally toward aircraft trailingedge devices, including devices having forwardly positioned hinge lines,and associated methods.

BACKGROUND

Modern high-speed aircraft generally have thin wings that provide a lowdrag profile during high-speed or cruise flight. The wings of theseaircraft often include various movable surfaces to provide aircraftcontrol and/or to configure the aircraft for low-speed operations (e.g.,take-off and landing). For example, in addition to carrying fuel, thewings of a high-speed transport aircraft typically include aileronsurfaces, spoiler surfaces, leading edge devices, and trailing edge flapsurfaces. These movable surfaces are often located at or near theleading and trailing edges of the wing, and are each movable between astowed position and a variety of deployed positions, depending upon theparticular flight condition of the aircraft.

FIG. 1A is a partially schematic illustration of a portion of anaircraft 10 a (in this case, a Boeing 767 aircraft) having a fuselage 11and a wing 20 with high lift devices configured in accordance with theprior art. The high lift devices can include deployable slats 21positioned toward the leading edge of the wing 20, and multiple trailingedge devices positioned toward the trailing edge of the wing 20. Thetrailing edge devices can include an outboard aileron 34, an outboardflap 32 a, an inboard aileron 60 a, and an inboard flap 31 a. Theinboard and outboard ailerons 60 a, 34 can be used generally for rollcontrol of the aircraft 10 a, and the inboard and outboard flaps 31 a,32 a can be used to control the lift of the aircraft 10 a at lowerspeeds (e.g., during take-off and landing). The ailerons 60 a, 34 aresimple hinged devices that are ungapped when in their deployedpositions. Conversely, when the inboard and outboard flaps 31 a, 32 aare deployed, they move in an aft direction to open a gap relative tothe wing 20. This aft motion is shown schematically by motion paths 41 aand 42 a, respectively. Because the inboard flap motion path 41 aconverges with the outboard flap motion path 42 a, the inboard aileron60 a located between the inboard flap 31 a and the outboard flap 32 adoes not move aft when deployed (as indicated by motion path 43 a) so asto avoid interference with the adjacent flaps 31 a, 32 a.

FIG. 1B is a cross-sectional illustration of the inboard aileron 60 a,illustrating the location of a hinge line 61 about which the inboardaileron 60 a pivots relative to the wing 20. Because the hinge line 61is located toward the front of the inboard aileron 60 a and within thecontour of the inboard aileron 60 a, a gap does not open between theinboard aileron 60 a and the wing when the inboard aileron 60 a deflectseither upwardly or downwardly. Instead, the leading edge 71 of theinboard aileron 60 a remains in close proximity to an aft-facing cove 37of the wing 20.

FIG. 1C is a partially schematic illustration of a portion of anotheraircraft 10 b (in this case, a Boeing 777 aircraft) having a fuselage 11and a wing 20 with high lift devices configured in accordance withanother prior art arrangement. The trailing edge devices can include aninboard flap 31 b, an outboard flap 32 b, and a flaperon 60 b, all ofwhich can travel aft during deployment to open corresponding gapsrelative to the wing 20. Accordingly, the inboard flap 31 b can travelaft along an inboard flap motion path 41 b, and the outboard flap 32 bcan move along a generally parallel outboard flap motion path 42 b.Because the inboard and outboard flap motion paths 41 b, 42 b aregenerally parallel, the flaperon 60 b can also move aft to a gappedposition along a flaperon motion path 43 b that is generally parallel tothe inboard and outboard flap motion paths 41 b, 42 b. Inboard spoilers51 and outboard spoilers 52 can be used as speed brakes and/or tocontrol the size of the gap between the wing 20 and the flaps 31 b, 32b.

An advantage of the arrangement shown in FIG. 1C when compared with thearrangement shown in FIGS. 1A and 1B is that the aft motion of theflaperon 60 b can allow it to be deployed to greater deflections withoutcausing flow separations, by virtue of the gap that opens between theflaperon 60 b and the wing 20. Accordingly, the flaperon 60 b can beoperated at high deflection rates for roll control, and at highdeflection angles for lift control. However, a potential drawback withthis arrangement is that complex mechanisms are typically required todeploy the flaperon 60 b to its aft configuration, particularly if themechanism is configured to fit within a shallow wing section, so as toreduce the size of external fairings. On the other hand, simplemechanisms (e.g., a simple hinge), tend to extend well beyond thecontours of the wing section, which requires relatively large, heavyhinge supports and associated fairings that generate drag. Accordingly,there is a need for improved, lightweight trailing edge devices.

SUMMARY

The following summary is provided for the benefit of the reader only,and is not intended to limit in any way the invention as set forth bythe claims. An aircraft system in accordance with one aspect of theinvention includes a wing and a trailing edge device coupled to thewing, with the trailing edge device being movable relative to the wingbetween a stowed position and a deployed position. The trailing edgedevice can have a leading edge, a trailing edge, an upper surface, and alower surface, with the upper surface having an intersection point withthe wing when the trailing edge device is in the stowed position. Themotion of the trailing edge device relative to the wing can includerotational motion about a hinge line positioned forward of theintersection point, and an airflow gap can be positioned between thetrailing edge of the wing and the leading edge of the trailing edgedevice when the trailing edge device is in the deployed position.

In further particular aspects, the hinge line can include a first hingeline, and the wing can include a spoiler positioned forward of thetrailing edge device, with the spoiler being pivotable relative to thewing about a second hinge line. The intersection point can be located ata point where the spoiler and the upper surface of the trailing edgedevice meet.

In still further aspects, the deployed position can include a firstdeployed position in which the trailing edge device is deflecteddownwardly relative to the stowed position, and the trailing edge devicecan be movable to a second deployed position in which the trailing edgedevice is deflected upwardly relative to the stowed position. Forexample, the trailing edge can be rotatable upwardly relative to thestowed position through an angle of up to 30°. When in the stowedposition, the trailing edge can be overlapped by a portion of the wing(e.g., the spoiler) by 20% or less of the chord length of the trailingedge device.

Further aspects are directed to a method for operating an aircraft wing.One such method can include moving a wing trailing edge device from astowed position to a deployed position by rotating the trailing edgedevice about a hinge line located forward of an intersection pointbetween the trailing edge device and the wing, so as to open an airflowgap between the wing and a leading edge of the trailing edge device. Themethod can further include allowing freestream air to pass through thegap while the trailing edge device is in the deployed position. Infurther particular aspects, flow surfaces of the trailing edge deviceexposed to the freestream flow adjacent to the wing are generally rigid,and moving the trailing edge device does not include changing a shape ofthe flow surfaces.

BRIEF DESCRIPTION OF THE DRAWINGS

FIGS. 1A-1C illustrate aircraft wings configured in accordance with theprior art.

FIG. 2 is an isometric illustration of an aircraft having a wing withtrailing edge devices configured in accordance with an embodiment of theinvention.

FIG. 3 is an enlarged, top plan view of one of wings shown in FIG. 2.

FIG. 4A is an enlarged plan view of a portion of the wing shown in FIG.3.

FIG. 4B illustrates trailing edge devices of the wing shown in FIG. 4Aat stowed and deployed positions.

FIGS. 5A-5C are schematic side illustrations of an intermediate trailingedge device in stowed and deflected positions in accordance with anembodiment of the invention.

FIG. 5D is a graph illustrating hinge point locations,non-dimensionalized by trailing edge device chord length, and locatedrelative to an intersection between the wing and the trailing edgedevice in accordance with several embodiments of the invention.

FIGS. 6A-6C are partially schematic, side elevation views of theintermediate trailing edge device shown in FIGS. 4A-4C, illustratingfurther features of this device.

DETAILED DESCRIPTION

The present disclosure describes aircraft trailing edge devices,including devices with non-parallel motion paths, and associatedmethods. Several specific details of the invention are set forth in thefollowing description and in FIGS. 2-6C to provide a thoroughunderstanding of certain embodiments of the invention. One skilled inthe relevant art, however, will understand that the present inventionmay have additional embodiments, and that other embodiments of theinvention may be practiced without several of the specific featuresdescribed below.

FIG. 2 is a partially schematic, isometric illustration of an aircraft210 having a fuselage 211 and wings 220 outfitted with trailing edgedevices 230 configured in accordance with an embodiment of theinvention. The aircraft 210 can further include an empennage 212 thatcarries horizontal stabilizers 213 and a vertical stabilizer 215. Thehorizontal stabilizers 213 can carry elevators 214, and the verticalstabilizer 215 can carry a rudder 216. The aircraft 210 can becontrolled by activating the trailing edge devices 230, the elevators214, and the rudder 216 under the direction of a control system 217(shown schematically in FIG. 2). Further details of the trailing edgedevices 230 are described below with reference to FIGS. 3-6C.

FIG. 3 is a top plan view of the left wing 220 of the aircraft 210initially described above with reference to FIG. 2. The wing 220 caninclude deployable leading edge devices, such as slats 221, located ator proximate to a leading edge 222 of the wing 220. The trailing edgedevices 230 are located aft of the leading edge 222 and form a compositetrailing edge 280. The trailing edge devices 230 can include an aileron234 positioned toward the outboard extremity of the wing 220, an inboardtrailing edge device 231 (e.g., an inboard flap) positioned toward theinboard extremity of the wing 220, an outboard trailing edge device 232(e.g., an outboard flap), and an intermediate trailing edge device 260(e.g., a flaperon) positioned between the inboard and outboard trailingedge devices 231, 232. Each of the trailing edge devices 230 can bemoved relative to the wing 220 between a stowed position (shown in FIG.3) and one or more deployed positions. In one aspect of this embodiment,the aileron 234 does not form a gap relative to the wing 220 when theaileron 234 is deployed, while the inboard, outboard and intermediatetrailing edge devices 231, 232, 260 do. The motions of the inboard,outboard and intermediate trailing edge devices (collectively referredto as “gapped trailing edge devices 238”) are described in greaterdetail below.

The inboard trailing edge device 231 can move along a first motion path241, the outboard trailing edge device 232 can move along a secondmotion path 242, and the intermediate trailing edge device 260 can movealong a third motion path 243. Each motion path may be purely rotationalwhen viewed from the side of the aircraft 210, or may be a combinationof rotation and translation. In either case, components of each motionpath carry the corresponding gapped trailing device 238 aft and downwardrelative to the wing 220, thereby opening a gap between the wing 220 andthe trailing edge device 238. The first motion path 241 can be orientedat a first angle A1 relative to the longitudinal axis 223 of theaircraft. In a particular aspect of an embodiment shown in FIG. 3, thefirst angle A1 can have a value of approximately zero degrees. Thesecond motion path 242 can be oriented at an angle A2 relative to thelongitudinal axis 223, and the third motion path 243 can be oriented atan angle A3 that has a value between A1 and A2. Accordingly, the motionpaths 241, 242, and 243 converge toward each other in an aft direction.

The wing 220 can further include spoilers 250 positioned proximate tothe gapped trailing edge devices 238. The spoilers 250 can includeoutboard spoilers 252, inboard spoilers 251, and an intermediate spoiler253. The spoilers 250 can be deployed in concert with the gappedtrailing edge devices 238 to provide for further control of the airflowadjacent to the trailing edge gaps. The spoilers 250 can also bedeployed independently of the motion of the gapped trailing edge devices238, for example, to provide a speed brake function. In a particularaspect of this embodiment, each of the spoilers 250 is a simple hingeddevice that rotates downwardly and upwardly relative to the wing 220(e.g., in the manner of standard aileron). Downward rotation can beaccomplished without opening an additional gap relative to the wing 220,and upward rotation may create a small gap. The trailing edges of thespoilers 250 can be aligned to form a generally monotonic profile bothwhen the spoilers 250 are in their stowed positions (as shown in FIG. 3)and also when the spoilers 250 are deployed downwardly.

FIG. 4A is a top plan view of a portion of the wing 220 shown in FIG. 3,approximately centered on the intermediate trailing edge device 260. Thewing 220 can include a rear spar 290, with the wing fuel volume locatedforward of the rear spar 290, and the gapped trailing edge devices 238located aft of the rear spar 290. Each of the gapped trailing edgedevices 238 can include at least one actuator for moving the trailingedge devices between their stowed and deployed positions. Accordingly,the inboard trailing edge device 231 can be coupled to an inboardactuator 244. The outboard trailing edge device 232 can be coupled to anoutboard actuator 245, and the intermediate trailing edge device 260 canbe coupled to an intermediate actuator 265. For purposes ofillustration, a single actuator is shown coupled to each of the gappedtrailing edge devices 238, but it will be understood by those ofordinary skill in the relevant art that each device 238 may be coupledto a multiple actuators in other embodiments. In any of theseembodiments, if the intermediate trailing edge device 260 is used forroll control (in addition to low-speed lift augmentation), while theinboard and outboard trailing edge devices 231, 232 are used generallyonly for low-speed lift augmentation, then the intermediate actuator 265can have a higher maximum actuation rate than that of the inboardactuator 244 and/or the outboard actuator 245. Accordingly, theintermediate actuator 265 can provide response times appropriate forperforming aileron functions.

Each of the gapped trailing edge devices 238 can include a leading edgepositioned close to the wing 220, and a distal trailing edge.Accordingly, the inboard trailing edge device 231 can include a firstleading edge 271 and a first trailing edge 281. The outboard trailingedge device 232 can include a second leading edge 272 and a secondtrailing edge 282. The intermediate trailing edge device 260 can includea third leading edge 273 and a third trailing edge 283. The leadingedges 271, 272 and 273 can form a composite device leading edge 270, andthe trailing edges 281, 282 and 283 can form the composite trailing edge280. In a particular aspect of this embodiment, each of the gappedtrailing edge devices 238 can undergo purely rotational motion byrotating about a hinge line that is generally parallel to thecorresponding leading edge. Accordingly, the first motion path 241 canbe generally normal to the first leading edge 271, the second motionpath 242 can be generally normal to the second leading edge 272, and thethird motion path 243 can be generally normal to the third leading edge273.

When the gapped trailing edge devices 238 are in their stowed positions(as shown in FIG. 4A), the corresponding trailing edges 281, 282, 283can form a generally continuous composite trailing edge 280 that definesa monotonically varying function. In this configuration, the leadingedges 271, 272, and 273 can be located beneath the correspondingspoilers 251, 252 and 253, respectively, as indicated by dashed lines inFIG. 4A. The leading edges 271, 272, 273 can each be swept bysuccessively greater angles (in a spanwise direction) relative to alateral axis 224 of the wing 220. Accordingly, the first leading edge271 can be swept by a first angle L1, the second leading edge 272 can beswept by an angle L2, and the third leading edge 273 can be swept by anangle L3 that is between L1 and L2. As is also shown in FIG. 4A, thefirst, second and third leading edges 271, 272, and 273 can be steppedrelative to each other when the gapped trailing edge devices 238 are intheir stowed positions. This is not expected to have an adverseaerodynamic consequence because the leading edges are positioned beneaththe corresponding spoilers when the gapped trailing edge devices 238 arein their stowed positions.

FIG. 4B is an enlarged, schematic illustration of the portion of thewing 220 shown in FIG. 4A, with the gapped trailing edge devices 238shown in stowed and selected deployed positions. The general outlines ofthe gapped devices 238 are shown in solid lines when the devices arestowed, dashed lines when the devices are partially deployed(corresponding to a take-off setting), and phantom lines when thedevices are fully deployed (corresponding to a landing setting). Asdescribed above, when the gapped devices 238 are in the stowedpositions, the trailing edges 281, 282, and 283 form a compositetrailing edge 280 that has a generally monotonically varying function.Although there may be small spaces between the sides of adjacent devices238, the overall composite trailing edge 280 does not includesignificant steps. Conversely, the composite leading edge 270 (formed bythe first leading edge 271, the second leading edge 272, and the thirdleading edge 273) is stepped and does not form a generally monotonicallyvarying function. As the gapped trailing edge devices 238 move fromtheir stowed positions to their deployed positions, the compositetrailing edge 280 becomes more stepped, and the composite leading edge270 becomes less stepped. For example, as shown by dashed lines in FIG.4B, when the gapped trailing edge devices 238 are in a partiallydeployed position (indicated by dashed lines), the leading edges 271,272, and 273 are more closely aligned with each other, while thetrailing edges 281, 282, and 283 depart from a generally monotonicallyvarying composite trailing edge 280. When the gapped trailing edgedevices 238 move to their fully deployed positions (as indicated byphantom lines in FIG. 4B), the composite leading edge 270 can describe agenerally monotonically varying function, while the composite trailingedge 280 is stepped. Accordingly, while spaces may exist between theedges of adjacent gapped trailing edge devices 238 at the compositeleading edge 270, the overall contour of the composite leading edge 270is generally monotonic and unstepped.

One feature of an arrangement of the gapped trailing edge devices 238 inaccordance with several embodiments of the invention is that all threeof the devices 238 can form aerodynamic gaps when moved to theirdeployed positions. An advantage of this arrangement is that the devices238 can be deployed to greater deflection angles than would be possibleif the devices were not gapped, which can in turn provide for greateraircraft control and reduced aircraft landing speeds.

Another feature of at least some of the foregoing embodiments is thatthey can include an intermediate, gapped trailing edge device 260 thathas a generally trapezoidal planform shape and that is positionedbetween two additional gapped trailing edge devices 231, 232. Thetrapezoidal shape can allow the intermediate trailing edge device 260 tobe fit between an inboard trailing edge device 231 located at a portionof the wing 220 that has little or no sweep, and an outboard trailingedge 232 device located at a portion of the wing 220 that has asignificant sweep angle. In addition, the intermediate trailing edgedevice 260 can move aft relative to the wing 220 along a motion paththat is aligned between the motion paths of the inboard and outboardtrailing edge devices 231, 232. This arrangement allows the intermediatetrailing edge device 260 to move downwardly and in some case, aft (by atleast a short distance), without interfering with the inboard andoutboard trailing edge devices 231,232, which are also moving aft. As aresult, the intermediate trailing edge device 260 can form a gaprelative to the wing 220, which increases its effectiveness at highdeflection angles without causing interference with the adjacentdevices. The overall effect of this arrangement is that it can makeincreased use of the trailing edge devices 238 when compared withexisting trailing edge device arrangements.

Still another feature of at least some embodiments of the foregoingarrangements is that they can include trailing edge devices having theforward 20% (or less) covered by spoilers or other portions of the wingwhen the trailing edge devices are stowed. An advantage of thisarrangement is that it can require less aftward movement to open asuitable gap between the wing and the trailing edge device when thetrailing edge device is deployed.

FIGS. 5A-5C schematically illustrate the intermediate trailing edgedevice 260, including features that can increase the ease with which thetrailing edge device 260 is integrated with the adjacent trailing edgedevices 231, 232 described above. Referring first to FIG. 5A, theintermediate trailing edge device 260 can have a hinge point 261 that islocated forward of the third leading edge 273 by a distance F. The hingepoint 261 can also be located below both an upper surface 269 and alower surface 268 of the intermediate trailing edge device 260. In aparticular embodiment, the hinge point 261 is located a distance D belowthe lower surface 268. In other embodiments, the location of the hingepoint 261 can be identified with reference to an intersection point Ibetween a portion of the wing 220 and the upper surface 269 of theintermediate trailing edge device 260. In an embodiment shown in FIG.5A, the intersection point I can be at the aft-most point of theintermediate spoiler 253, and in other embodiments (e.g., those in whichthe wing 220 does not include a spoiler at this location), theintersection point I can be at another portion of the wing 220. In anyof these embodiments, the hinge point 261 can be located a distance D1beneath the intersection point I, and a distance F1 forward of theintersection point I.

By locating the hinge point 261 forward of the leading edge 273 (and/orthe intersection point I), and at a relatively shallow depth D (or D1)below the intermediate trailing edge device 260, the motion of theintermediate trailing edge device 260 when it deploys can be less likelyto interfere with the motion of adjacent trailing edge devices. Inparticular, this arrangement can allow a significant portion of themovement of the intermediate trailing edge device 260 to be downward (inaddition to being aftward) when it is deployed (as shown in FIG. 5B).For example, in this arrangement, the leading edge 273 of theintermediate trailing edge device 260 can move downwardly by asignificant margin as a result of the hinge point 261 being positionedforward relative to the leading edge 273. This is unlike many existingtrailing edge devices which have hinge points located at or behind theleading edge. An advantage of this arrangement is that the intermediatetrailing edge device 260 can form an aerodynamically significant gap 262while moving along an intermediate flap motion path 243 (shown in FIG.3) that does not interfere with the motion of adjacent trailing edgedevices.

The surfaces of the intermediate trailing edge device 260 (e.g., thelower surface 268 and the upper surface 269) can be generally rigid inat least one embodiment, and accordingly do not change shapesignificantly when the intermediate trailing edge device 260 isdeployed. This is unlike some other trailing edge devices that changeshape during deployment. In one aspect of this embodiment the positionof the hinge point 261 can allow the intermediate trailing edge device260 to open the gap 262 when deployed, without the need for flexibleflow surfaces.

The size of the gap 262 can be controlled at least in part by theintermediate spoiler 253. The intermediate spoiler 253 can rotate abouta spoiler hinge point 254, and can follow (at least in part) the motionof the trailing edge device 260 when the trailing edge device 260 isdeflected downwardly (as shown in FIG. 5B). When the trailing edgedevice 260 is deflected upwardly (as shown in FIG. 5C), the spoiler 253can also follow this motion in such a manner as to eliminate or nearlyeliminate the gap 262. Accordingly, the spoiler 253 can follow a motionpath that nearly seals it against the trailing edge device 260, withoutcausing the spoiler 253 to actually rub against the trailing edge device260. In other embodiments, such rubbing can be permitted so long as itdoes not damage either the spoiler 253 or the trailing edge device 260.This arrangement can allow the trailing edge device 260 to be deflectedupwardly for roll control and/or wing load alleviation. The intermediatespoiler 253 can also be operated independently of the trailing edgedevice 260 (as shown in dashed lines in FIG. 5A), to act as a spoilerand/or speed brake. In particular embodiments, the trailing edge device260 can be deflected upwardly by at least 10° relative to the stowedposition, and in further particular embodiments, the trailing edgedevice 260 can be deflected upwardly by up to 30°.

As discussed above with reference to FIG. 4A, the intermediate spoiler253 can overlap the intermediate trailing edge device 260 when bothelements are in their respective stowed positions. In a particularembodiment, the overlap distance 0 (shown in FIG. 5A) can be 20% or lessof the chord length C (FIG. 5A) of the intermediate trailing edge device260. An advantage of an embodiment of this arrangement is that theintermediate trailing edge device 260 need not move aft by a significantamount in order to move away from the intermediate spoiler 253 and opena gap.

In particular embodiments, the distances F1 and D1 described above withreference to FIG. 5A can have specific ranges of values, whennon-dimensionalized relative to each other and/or relative to the chordlength C of the intermediate trailing edge device 260. For example, FIG.5D illustrates representative hinge points 261 plotted on anon-dimensional grid. Point I (the origin) identifies the intersectionpoint between the wing 220 and the upper surface 269 of the intermediatetrailing edge device 260. The x-scale identifies the fore/aft locationof the hinge points 261, non-dimensionalized by the chord length C ofthe intermediate trailing edge device 260. The y-scale identifies theupward/downward location of the hinge points 261, alsonon-dimensionalized by the chord length C. Hinge points 261 inaccordance with particular aspects of the invention are located forwardof and above line 259. Accordingly, these hinge points 261 can bedescribed as being forward of and above a series of line segmentspassing through x, y coordinates (0.5, −0.5), (0.1 −0.2), (0.2, −0.3),(0.5 −0.4) and (1.0, −0.5) identified as points 258 a-258 e,respectively.

Returning to FIG. 5A, the rear spar 290 can be positioned relatively farforward of the intermediate trailing edge device 260. For example, therear spar 290 can be positioned a distance S forward of the thirdleading edge 273. A ratio of S to local streamwise chord length C canhave a value of about 0.5. In some cases, this ratio can be higher aswell. While this ratio can apply to the intermediate trailing edgedevice 260 (and in particular, the outboard edge of the intermediatetrailing edge device 260), it can also apply to the outboard trailingedge device 232 shown in FIG. 3, at any point along the span of thatdevice.

The foregoing ratio (e.g., as applied to the outboard trailing edgedevice 232) is unlike many existing arrangements in which the ratio ofS/C varies from about 0.2 to about 0.32. An advantage of an embodimentof the arrangement shown in FIG. 5A is that it can accommodate a forwardlocation of the hinge point 261 (and associated actuation mechanisms)without significantly impacting overall fuel volume. This in turn canimprove the integration of the outboard trailing edge device 232.

FIGS. 6A-6C illustrate further details of the operation of theintermediate trailing edge device 260. FIG. 6A illustrates theintermediate trailing edge device 260 in its stowed position. Inaddition to the components described above, the aircraft wing 220 caninclude a lower cove door 263 that controls airflow along the lowersurface of the trailing edge device 260. As shown in FIG. 6B, theintermediate trailing edge device 260 has been moved to a lower deployedposition to open the gap 262 between the leading edge 273 and the wing220. Accordingly, the actuator 265 drives an actuator link 266 aft tomove the intermediate trailing edge device 260 along its motion path243. The lower cove door 263 can be mechanically linked to the couplingbetween the actuator 265 and the intermediate trailing edge device 260to rotate out of the way and open the gap 262, allowing air (indicatedby arrow A) to flow through. The intermediate spoiler 253 can also bemechanically linked to the motion of the intermediate trailing edgedevice 260 to rotate downwardly and control the size of the gap 262. Inother embodiments, the motion of the lower cove door 263 and/or theintermediate spoiler 253 can be controlled in other fashions, forexample, by an independent hydraulic or electric control system. FIG. 6Cillustrates the intermediate trailing edge device 260 and theintermediate spoiler 253 deflected upwardly, for example, whileperforming a roll control or wing load alleviation function. As is alsoshown in FIG. 6C, making the depth of the hinge 261 relatively shallowcan reduce or eliminate the need for a large or otherwise extensivefairing at the lower surface of the wing 220. The combination of agapped trailing edge device with a drooped spoiler can improve both theaerodynamic performance of the high lift system and the wing in which itis installed.

In a particular embodiment, the arrangement shown in FIGS. 6A-6C caninclude a cam track 291 and associated linkage that attach theintermediate spoiler 253 to the intermediate trailing edge device 260,controlling the gap 262 between the two devices. By tailoring thecontour of the cam surfaces of the cam track 291, the position of theintermediate spoiler 253 relative to the intermediate trailing edgedevice 260 (including the gap 262) can be specified with a high degreeof accuracy throughout the entire range of motion. The cam track 291 canadd specific advantages over other embodiments, such as hydraulic orelectric actuators, or a bellcrank mechanism. For example, actuators(hydraulic or electric) may be heavier, and/or more costly, than the camtrack 291. A bell crank, though similar in weight and reliability to thecam track 291, typically does not match the flexibility and adaptabilityof the cam track 291 to manage the gap 262. In a particular aspect of anembodiment shown in FIGS. 6A-6C, the cam track 291 can improve theability of the spoiler 253 to fair to the intermediate trailing edgedevice 260 in the retracted position. The cam track 291 can also aid insetting the gap 262 at a certain value for given down positions of theintermediate trailing edge device 260 (e.g., a takeoff position and alanding position). The cam track 291 can also provide control forspecific movement patterns. For example, when the intermediate trailingedge device 260 moves down from the cruise (retracted) position, the camtrack 291 can be shaped so that the spoiler 253 “dwells,” allowing thegap 262 to increase quickly as the intermediate trailing edge device 260moves down. Similarly, as the intermediate trailing edge device 260moves up from the cruise (retracted) position, the spoiler 253 canquickly move upwards, to clear the rising intermediate trailing edgedevice 260.

From the foregoing, it will be appreciated that specific embodiments ofthe invention have been described herein for purposes of illustration,but that various modifications may be made without deviating from theinvention. For example, in some embodiments, the intermediate trailingedge device can be installed between inboard and outboard trailing edgedevices and can have a gapped deployed configuration that is driven byarrangements other than those shown in the Figures. The trailing edgedevices, including the intermediate trailing edge device, can bedeployed to control a spanwise lift distribution over the wing. Motionof the trailing edge devices in several embodiments includes rotationalmotion. In at least some embodiments, the motion of the trailing edgedevices can also include other motions (e.g., linear motions). Aspectsof the invention described in context of particular embodiments may becombined or eliminated in other embodiments. For example, aspects of theinvention described in the context of three gapped trailing edge devicescan be extended to a greater number of gapped trailing edge devices inother embodiments. Further, while advantages associated with certainembodiments of the invention have been described in the context of thoseembodiments, other embodiments may also exhibit such advantages, and notall embodiments need necessarily exhibit such advantages to fall withinthe scope of the invention. Accordingly, the invention is not limited,except as by the appended claims.

1. An aircraft system, comprising: a wing; and a trailing edge devicecoupled to the wing, the trailing edge device being movable relative tothe wing between a stowed position and a deployed position, the trailingedge device having a leading edge, a trailing edge, an upper surface anda lower surface, the upper surface having an intersection point with thewing when the trailing edge device is in the stowed position; whereinthe motion of the trailing edge device relative to the wing includesrotational motion about a hinge line positioned forward of theintersection point; and wherein an airflow gap is positioned between atrailing edge of the wing and the leading edge of the trailing edgedevice when the trailing edge device is in the deployed position.
 2. Theaircraft system of claim 1 wherein: the trailing edge device has a chordlength C between the leading and trailing edges of the trailing edgedevice; and wherein on a graph depicting locations forward and aft ofthe intersection point along an x-axis, and locations above and belowthe intersection point along a y-axis, the hinge point is positionedforward of and above a series of generally straight line segments linepassing through the following coordinates: (0.5*C, −0.5*C), (0.1*C,−0.2*C), (0.2*C, −0.3*C), (0.5*C, −0.4*C), and (1.0*C, −0.5*C).
 3. Theaircraft system of claim 1 wherein the hinge line is a first hinge line,and wherein the wing includes a spoiler positioned forward of thetrailing edge device, the spoiler being pivotable relative to the wingabout a second hinge line to follow a motion of the trailing edge deviceboth upwardly and downwardly from a neutral position, and wherein theintersection point is located at a point where the spoiler and the uppersurface of the trailing edge device meet.
 4. The aircraft system ofclaim 1 wherein the deployed position is a first deployed position inwhich the trailing edge device is deflected downwardly relative to thestowed position, and wherein the trailing edge device is movable to asecond deployed position in which the trailing edge device is deflectedupwardly relative to the stowed position.
 5. The aircraft system ofclaim 4 wherein the trailing edge device is rotatable upwardly relativeto the stowed position through an angle of up to 30 degrees.
 6. Theaircraft system of claim 1 wherein the trailing edge device has a devicechord length, and wherein a portion of the wing overlaps the trailingedge device by 20% or less of the device chord length when the trailingedge device is in the stowed position.
 7. The aircraft system of claim 1wherein the trailing edge device does not include a flexible flowsurface that is exposed to the freestream flow adjacent to the wing andthat changes shape as the trailing edge moves from the stowed positionto the deployed position.
 8. The aircraft system of claim 1 wherein thehinge line is positioned forward of the leading edge of the trailingedge device.
 9. The aircraft system of claim 1 wherein the hinge line isa first hinge line, and wherein the wing includes a spoiler positionedforward of the trailing edge device, the spoiler being pivotablerelative to the wing about a second hinge line, and wherein theintersection point is located at a point where the spoiler and the uppersurface of the trailing edge device meet.
 10. The aircraft system ofclaim 9 wherein the spoiler is mechanically coupled to the trailing edgedevice to move in a coordinated fashion with the trailing edge device.11. The aircraft system of claim 9, further comprising a door coupled tothe wing proximate to a lower surface of the wing, the door beingmovable relative to the trailing edge device between a stowed positionin which the door provides a seal between the lower surface of the wingand the leading edge of the trailing edge device, and a deployedposition in which the door is spaced apart from the leading edge of thetrailing edge device.
 12. The aircraft system of claim 1, furthercomprising a door coupled to the wing proximate to a lower surface ofthe wing, the door being movable relative to the trailing edge devicebetween a stowed position in which the door provides a seal between thelower surface of the wing and the leading edge of the trailing edgedevice, and a deployed position in which the door is spaced apart fromthe leading edge of the trailing edge device.
 13. The aircraft system ofclaim 12 wherein the door is mechanically coupled to the trailing edgedevice to move in a coordinated fashion with the trailing edge device.14. The aircraft system of claim 1 wherein the trailing edge deviceincludes a flaperon, and wherein the system further comprises: a flapcoupled to the wing proximate to the flaperon, the flap being movablerelative to the wing between a stowed position and a deployed position;a first actuator coupled between the wing and the flaperon, the firstactuator having a first maximum actuation rate; and a second actuatorcoupled between the wing and the flap, the second actuator having asecond maximum actuation rate that is less than the first.
 15. Theaircraft system of claim 1 wherein the wing includes a first wing, andwherein the system further comprises: a second wing; a fuselage coupledto the first and second wings; and an empennage coupled to the fuselage.16. An aircraft, comprising: a fuselage; an empennage coupled to thefuselage; a wing; and a trailing edge device coupled to the wing, thetrailing edge device having a leading edge, a trailing edge, a generallyrigid upper surface extending from the leading edge to the trailingedge, a generally rigid lower surface extending from the leading edge tothe trailing edge, and a chord length C extending from the leading edgeto the trailing edge between the upper and lower surfaces, the trailingedge device being movable relative to the wing between a stowedposition, a first deployed position in which the trailing edge device ismoved downwardly from the stowed position, and a second deployedposition in which the trailing edge device is moved upwardly from thestowed position; a spoiler positioned forward of the trailing edgedevice, the spoiler being pivotable relative to the wing about a secondhinge line to follow a motion of the trailing edge device both upwardlyand downwardly from the stowed position; wherein the upper surface hasan intersection point with the spoiler when the trailing edge device isin the stowed position; the motion of the trailing edge device relativeto the wing includes rotational motion about a first hinge line that ispositioned (a) forward of the intersection point, and (b) below theintersection point; on a graph depicting locations forward and aft ofthe intersection point along an x-axis, and locations above and belowthe intersection point along a y-axis, the hinge point is positionedforward of and above a series of generally straight line segments linepassing through the following coordinates: (0.5*C, −0.5*C), (0.1*C,−0.2*C), (0.2*C, −0.3*C), (0.5*C, −0.4*C), and (1.0*C, −0.5*C); andwherein an airflow gap is positioned between a trailing edge of the wingand a leading edge of the trailing edge device when the trailing edgedevice is in at least one deployed position.
 17. The system of claim 16wherein the first hinge line is positioned forward of the leading edgeof the trailing edge device.
 18. The system of claim 16 wherein thespoiler is mechanically coupled to the trailing edge device to move in acoordinated fashion with the trailing edge device, and wherein thesystem further comprises a cam track positioned to guide the motion ofthe trailing edge device.
 19. A method for operating an aircraft wing,comprising: moving a wing trailing edge device from a stowed position toa deployed position by rotating the trailing edge device about a hingeline located forward of an intersection point between the trailing edgedevice and an upper surface of the wing so as to open an airflow gapbetween the leading edge and the wing; and allowing freestream air topass though the gap while the trailing edge device is in the deployedposition.
 20. The method of claim 19 wherein rotating the trailing edgedevice includes rotating the trailing edge device about a hinge linelocated forward of a leading edge of the trailing edge device.
 21. Themethod of claim 19 wherein moving the trailing edge device includesrotating the trailing edge device downwardly from the stowed position,and wherein the method further comprises rotating the trailing edgedevice upwardly from the stowed position.
 22. The method of claim 19,further comprising actively controlling a rolling motion of the aircraftby deflecting the trailing edge device.
 23. The method of claim 19,further comprising actively controlling a spanwise lift distributionover the wing by deflecting the trailing edge device.
 24. The method ofclaim 19 wherein the trailing edge device has a device chord length, andwherein the method further comprises stowing the trailing edge device bypositioning the trailing edge device with the wing overlapping thetrailing edge device by 20% or less of the device chord length.
 25. Themethod of claim 19 wherein flow surfaces of the trailing edge deviceexposed to the freestream flow adjacent to the wing are generally rigid,and wherein moving the trailing edge device does not include a changinga shape of the surfaces.